JP3095180B2 - Molding process of preforms for the production of thermostructural composite parts, in particular woven parts or panels - Google Patents

Molding process of preforms for the production of thermostructural composite parts, in particular woven parts or panels

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Publication number
JP3095180B2
JP3095180B2 JP03076446A JP7644691A JP3095180B2 JP 3095180 B2 JP3095180 B2 JP 3095180B2 JP 03076446 A JP03076446 A JP 03076446A JP 7644691 A JP7644691 A JP 7644691A JP 3095180 B2 JP3095180 B2 JP 3095180B2
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JP
Japan
Prior art keywords
preform
process according
stiffener
cover layer
forming device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
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JP03076446A
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Japanese (ja)
Other versions
JPH04224177A (en
Inventor
ビブ ミッシェル
ルイ リムジン ジャン
Original Assignee
ソシエテ・ナシオナル・デテユード・エ・ドウ・コンストリユクシオン・ドウ・モトール・ダヴイアシオン、“エス．エヌ．ウ．セ．エム．アー．”
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Publication of JPH04224177A publication Critical patent/JPH04224177A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/71—Ceramic products containing macroscopic reinforcing agents
    • C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
    • C04B35/80—Fibres, filaments, whiskers, platelets, or the like
    • C04B35/83—Carbon fibres in a carbon matrix
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/024—Woven fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/06—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by a fibrous or filamentary layer mechanically connected, e.g. by needling to another layer, e.g. of fibres, of paper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/02—Physical, chemical or physicochemical properties
    • B32B7/027—Thermal properties
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
    • C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
    • C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/62865—Nitrides
    • C04B35/62868—Boron nitride
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/62873—Carbon
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/71—Ceramic products containing macroscopic reinforcing agents
    • C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
    • C04B35/80—Fibres, filaments, whiskers, platelets, or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2255/00—Coating on the layer surface
    • B32B2255/02—Coating on the layer surface on fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/105—Ceramic fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/16—Submarines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2607/00—Walls, panels
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5244—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5248—Carbon, e.g. graphite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/365—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S427/00—Coating processes
    • Y10S427/10—Chemical vapor infiltration, i.e. CVI

Description

【発明の詳細な説明】DETAILED DESCRIPTION OF THE INVENTION

【０００１】[0001]

【産業上の利用分野】本発明は、熱構造的複合材料部品
の製造に関し、特に繊維状の予成形物(preforms)を予成
形物の気孔内でマトリックスを使って化学的蒸気蒸着に
より高密度化した織物状部品又はパネルの製造に関す
る。FIELD OF THE INVENTION The present invention relates to the manufacture of thermostructural composite parts, and more particularly, to high density fibrous preforms by chemical vapor deposition using a matrix within the pores of the preform. The manufacture of woven textile parts or panels.

【０００２】熱構造的複合材料とは、構造部材を形成す
るために必要な機械的性質を有し、その性質を高温で保
持する材料を指すものと理解される。このような材料と
しては、炭素マトリックスで高密度化した繊維状の予成
形物で作った炭素−炭素（Ｃ−Ｃ）複合材や、セラミッ
ク・マトリックスで高密度化した耐火繊維状の予成形物
で作ったセラミック・マトリックス（ＣＭＣ）複合材
（炭素又はセラミック繊維）などが代表的である。ＣＭ
Ｃでは、マトリックス並びに強化繊維にもっともよく使
われるセラミック材料は炭化ケイ素である。炭素及び炭
化ケイ素の化学的蒸気蒸着工程は技術的に周知で、ＵＳ
−Ａ−３８９５ ０８４及びＦＲ−Ａ−２４０１ ８８
８等に開示されている。[0002] A thermostructural composite material is understood to mean a material that has the mechanical properties necessary to form a structural member and retains that property at high temperatures. Such materials include carbon-carbon (CC) composites made of fibrous preforms densified with a carbon matrix, and refractory fibrous preforms densified with a ceramic matrix. A typical example is a ceramic matrix (CMC) composite material (carbon or ceramic fiber) made by the above. CM
In C, the most commonly used ceramic material for the matrix as well as the reinforcing fibers is silicon carbide. Chemical vapor deposition processes for carbon and silicon carbide are well known in the art and are described in US Pat.
-A-3895 084 and FR-A-2401 88
8 and the like.

【０００３】複合材料の強化材を構成する繊維状予成形
物は、フエルトや布、平行に並べた繊維の層等、様々な
繊維状織物で作ることができる。このような織物を何層
かに配列し、周知の技術によって針で縫ったり糸を縫い
込んだりすることで結合させる。高密度化の準備とし
て、通常はグラファイト製の成形工具に繊維状予成形物
を設置し、この成形工具が製造する部品の形に応じて繊
維状予成形物を所望の形に保持するが、この工具はまた
必要な繊維体積率（予成形物の見掛け体積に対して繊維
が有効に占める部分）を得るため予成形物を圧縮するの
に使用することもできる。[0003] The fibrous preforms that make up the composite reinforcement can be made of various fibrous fabrics, such as felt, cloth, and layers of fibers arranged in parallel. Such woven fabrics are arranged in several layers, and are joined by sewing with a needle or thread by a well-known technique. As a preparation for densification, usually a fibrous preform is placed on a graphite forming tool, and the fibrous preform is held in a desired shape according to the shape of a part manufactured by the forming tool. The tool can also be used to compress the preform to obtain the required fiber volume fraction (the effective portion of the fiber relative to the apparent volume of the preform).

【０００４】第１段階では、マトリックス形成材の化学
的蒸気蒸着を行い、予成形物を十分に強固化する。すな
わち、予成形物を取り扱う際、成形工具を使わないで予
成形物の形状を保持できるよう繊維を十分に結合させ
る。こうして強固化した予成形物は工具から取り外す事
ができるので、必要な高密度化が得られるまで化学的蒸
気蒸着工程を行うことができる。In the first stage, chemical vapor deposition of the matrix-forming material is performed to sufficiently solidify the preform. That is, when handling the preform, the fibers are sufficiently bonded so that the shape of the preform can be maintained without using a molding tool. The solidified preform can be removed from the tool so that the chemical vapor deposition process can be performed until the required densification is obtained.

【０００５】[0005]

【従来の技術】比較的大型の織物状部品又はパネルの製
造では、強固化の段階で問題がある。すなわち、部品が
大きいことや厚みが比較的少ないこと、並びに多数のス
チフナを組み込まなければならないことから、グラファ
イト製の成形工具には非常に複雑なものを使用する必要
がある。このような工具は、予成形物の表面を覆ってこ
れを一定の形に保ち必要な圧縮を行う一方で、スチフナ
を織物上に保持するため、多くの部品から構成される。
スチフナは高密度化段階で組み込まれることになる。ス
チフナ自身は前もって高密度化あるいは強固化されてお
り、部品の残りの部分との結合は共高密度化によって行
う。共高密度化において、マトリックス材は部品との接
合面でマトリックスの連続性によってスチフナをパネル
又は織物に有効に「接着」する。BACKGROUND OF THE INVENTION In the manufacture of relatively large woven parts or panels, there are problems during the consolidation stage. That is, since the parts are large, the thickness is relatively small, and a large number of stiffeners must be incorporated, it is necessary to use a very complicated graphite forming tool. Such a tool is composed of many parts in order to keep the stiffener on the fabric, while covering the surface of the preform and keeping it in the required shape and providing the necessary compression.
The stiffener will be incorporated at the densification stage. The stiffener itself has been densified or hardened in advance, and the connection with the rest of the part is made by co-densification. In co-densification, the matrix material effectively "glues" the stiffener to the panel or fabric due to the continuity of the matrix at the interface with the component.

【０００６】[0006]

【発明が解決しようとする課題】このような工具は製造
に時間と費用がかかり、組み立ても複雑である。また、
このような工具は、高密度化の際、部品の製造に使用す
るマトリックス材が付着するため、工具を再使用する度
に前もって修復する必要がある。工具の寸法が変った
り、再使用することができない程度まで劣化することが
あるため、このような修復を頻繁に繰り返すことはでき
ない。その結果、このような工具は数回使用しただけで
廃棄されているため、製造する部品のコストが非常に高
いものとなっている。最後に、高密度化の際、工具に送
り穴があるにも拘わらず支持具の一部が予成形物を覆っ
てしまうことがあり、このため予成形物の気孔への浸透
ガスの浸透が妨げられ、高密度化が均一でなくなる。Such tools are time consuming and expensive to manufacture and complicated to assemble. Also,
Such tools need to be repaired in advance each time the tool is reused, as the matrix material used to manufacture the parts will adhere to it during densification. Such repairs cannot be repeated frequently because the dimensions of the tool may change or deteriorate to the point that it cannot be reused. As a result, such tools are discarded after only a few uses, and the cost of the parts to manufacture is very high. Finally, during densification, a part of the support may cover the preform even though the tool has a perforation hole. Hindered and the densification is not uniform.

【０００７】[0007]

【課題を解決するための手段】本発明はこのような点に
鑑みてなされたものであり、簡易化した工具によって予
成形物を成形する工程、特にスチフナを組み込んだもの
を含む織物状の部品やパネルの製造工程の提供を目的と
する。本発明では上記課題を解決するために、予成形物
を横切って成形装置の穴を通る糸によって固定成形装置
に予成形物を結合して予成形物成形をする工程が提供さ
れる。従って、この固定工具は予成形物の片面を当てる
成形装置に限られ、予成形物を成形装置に結合（又は縫
いつけ）することによって予成形物の形を保ち圧縮す
る。上記結合に使用する糸は、化学的蒸気蒸着段階でも
完全性を保つ炭素又はセラミックの糸が好ましい。予成
形物の高密度化、又は少なくとも強固化後、結合糸を破
壊することによって成形装置から予成形物を取り出す。
結合糸は部品に縫い込まれたまま残り、積層間セン断
（すなわち部品両面に平行なセン断）に対しては特に有
効な強化材となる。SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and has been made in consideration of the above circumstances, and has been made in view of the step of forming a preform with a simplified tool, particularly a woven part including a stiffener-incorporated part. And manufacturing process of panels. In order to solve the above-mentioned problems, the present invention provides a step of forming a preform by joining the preform to a fixed molding device by a thread passing through a hole of the molding device across the preform. Therefore, the fixing tool is limited to a molding device that applies one side of the preform, and the preform is maintained in shape and compressed by bonding (or sewing) the preform to the molding device. The yarn used for the bonding is preferably a carbon or ceramic yarn that maintains its integrity during the chemical vapor deposition stage. After densification, or at least consolidation, of the preform, the preform is removed from the forming apparatus by breaking the binding yarn.
The binding yarn remains sewn into the part and is a particularly effective reinforcement for shear between laminations (ie, shear parallel to both sides of the part).

【０００８】有利には、結合前に、予成形物の成形装置
に面した方とは反対の面にカバー層を設置する。このカ
バー層は、耐火繊維から作ったキャンバス又はサテン織
りの布のような２次元繊維材で、その目的は、結合糸に
よって予成形物の表面全体に生じる圧縮力を分散させる
ことである。カバー層の織物は十分に空気を通して、気
体が予成形物に容易かつ均一に浸透するようにする。Advantageously, before bonding, a cover layer is provided on the side opposite to the side facing the molding device for the preform. The cover layer is a two-dimensional fibrous material, such as a canvas or a satin woven fabric made from refractory fibers, the purpose of which is to distribute the compressive forces created by the binding yarn over the entire surface of the preform. The fabric of the cover layer is sufficiently air-permeable to allow the gas to easily and uniformly penetrate the preform.

【０００９】カバー層は、予成形物とは異なる膨張率を
持つ材料で作ることができる。化学的蒸気蒸着による高
密度化は比較的高温で行うため、浸透後に冷却する際、
カバー層と予成形物の膨張率の違いによって、マトリッ
クス材によって共に浸透させた予成形物とカバー層間の
接合面に破断が生じる。そうすると、予成形物の強固化
が終わった時カバー層を容易に予成形物から分離でき
る。主にカバー層上に形成される表面コーティングはカ
バー層を予成形物から引き出すことで除去することがで
きる。その結果、予成形物のデスケーリングをしなくて
も、予成形物の中心部の気孔が容易に侵入可能となって
高密度化を継続することができる上、表面状態が均質か
つ均一になる。有利には、各要素を予成形物に結合させ
る結合糸によって、要素を予成形物に一体化できる。こ
れによって、例えば、一体式のスチフナを装着した織物
やパネルの製造において、スチフナと織物又はパネルを
結合させた共高密度化がこの結合糸によって有利に強化
される。[0009] The cover layer can be made of a material having a different coefficient of expansion than the preform. Densification by chemical vapor deposition is performed at a relatively high temperature, so when cooling after infiltration,
Due to the difference in the coefficient of expansion between the cover layer and the preform, a fracture occurs at the joint surface between the preform and the cover layer, both impregnated with the matrix material. Then, the cover layer can be easily separated from the preform when the preform has hardened. The surface coating formed primarily on the cover layer can be removed by withdrawing the cover layer from the preform. As a result, the pores at the center of the preform can easily penetrate without continuing the descaling of the preform, and the densification can be continued, and the surface state becomes uniform and uniform. . Advantageously, the elements can be integrated into the preform by means of binding yarns which connect each element to the preform. Thereby, for example, in the manufacture of fabrics and panels with integrated stiffeners, the co-densification of the connection of the stiffeners with the fabric or panel is advantageously enhanced by the binding yarn.

【００１０】[0010]

【実施例】一体式スチフナを装着した比較的大型のパネ
ルの熱構造的複合材料構造材の製造における本発明の工
程の実施例を以下に説明する。このパネルは、例えば作
業中高温にさらされる宇宙船の構造材を形成するもので
ある。パネルの予成形物１０（図１）は、耐火繊維（炭
素又はセラミック）製織物の層を重ね合わせて製造す
る。この層は、例えば布やフエルトの層、平行に向けた
糸の層、あるいは布の層や網状にした繊維の層を前もっ
て縫ったものの合成体などで構成される。これらの層は
縫込むことで結合させることができる。予成形物１０の
片面１０ａは、製造するパネルの形に合せた工具要素を
形成する固定成形装置１２に当てられている。成形装置
１２はグラファイト製で、片面１０ａに気体が浸透する
よう多数の穴１４があけられている。予成形物１０の片
面１０ａの反対側の片面１０ｂには、比較的通気のよい
キャンバスやサテンを外装した布等で作ったカバー層１
６が取り付けられている。このカバー層１６は、好まし
くは予成形物と異なる膨張率を有する材料から作る。そ
のため、セラミック繊維をベースとした予成形物を使用
する場合、この層は炭素繊維をベースとした布で作るこ
とができる一方、予成形物１０を炭素ベースの布とした
場合、層１６は炭化ケイ素繊維で作った繊維、あるいは
炭化ケイ素等のセラミック材料を繊維に付着させた炭化
ケイ素製の布とする。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An example of the process of the present invention in the manufacture of a thermostructural composite structure for a relatively large panel with an integrated stiffener is described below. This panel, for example, forms the structural material of a spacecraft that is exposed to high temperatures during operation. The panel preform 10 (FIG. 1) is manufactured by superimposing layers of a fabric made of refractory fibers (carbon or ceramic). This layer may be, for example, a layer of cloth or felt, a layer of threads oriented in parallel, or a composite of previously sewn layers of cloth or meshed fibers. These layers can be joined by sewing. One side 10a of the preform 10 is applied to a fixed forming device 12 which forms a tool element according to the shape of the panel to be manufactured. The molding device 12 is made of graphite, and has a large number of holes 14 so that gas can permeate one surface 10a. On one side 10b of the preform 10 opposite to the one side 10a, a cover layer 1 made of a relatively air-permeable canvas or a cloth coated with satin is used.
6 is attached. This cover layer 16 is preferably made of a material having a different expansion coefficient than the preform. Thus, if a preform based on ceramic fibers is used, this layer can be made of a cloth based on carbon fibers, while if the preform 10 is a cloth based on carbon, layer 16 will be carbonized. A fiber made of silicon fiber or a silicon carbide cloth in which a ceramic material such as silicon carbide is adhered to the fiber.

【００１１】複数のスチフナ２０（図１には１つのみ示
す）を予成形物１０に一体化する。図のスチフナでは側
面がＩ字形になって、基部の一方が予成形物１０にかか
っている。スチフナ２０は予成形物１０と同じ性質の繊
維強化織物製で、望ましくは製造するパネルと同様、前
もってマトリックスで高密度化（強固化）しておくこと
ができる。このように強固化したスチフナ２０は、高密
度化が完了すれば予成形物１０の高密度化中でも取り扱
うことができる。A plurality of stiffeners 20 (only one is shown in FIG. 1) are integrated into the preform 10. In the stiffener shown, the side surface is I-shaped and one of the bases rests on the preform 10. The stiffener 20 is made of a fiber-reinforced fabric having the same properties as the preform 10, and can be densified (solidified) in advance in a matrix, preferably like a panel to be manufactured. The stiffener 20 thus solidified can be handled during the densification of the preform 10 if the densification is completed.

【００１２】図１に示すように、スチフナ２０は基部２
０の翼部２２ａ、２２ｂを予成形物１０を構成する層に
挿入することによって一体化している。そのため、２つ
の翼部分２２ａ、２２ｂが予成形物の２つの層の間に収
るよう、予成形物にはスチフナを設置する厚さ部分に切
開部が設けられている。そのため、各翼部２２ａ、２２
ｂは、スチフナの中心２４まで延びる予成形物１０の一
部に覆われる。同じく、カバー層１６はスチフナ２０の
ところで中断され、スチフナの翼部の上を中心２４まで
延びる。予成形物１０は、カバー層１６及び予成形物１
０を横切り、成形装置の穴１４又は少なくともその一部
を通過する糸３０による結合によって成形装置１２に保
持されている。図１に示す例では、糸は、成形装置１
２、予成形物１０及びカバー層１６からなる組立品の片
面と他面の間を交互に通過する縫い線を形成している。As shown in FIG. 1, the stiffener 20 is
The zero wings 22a and 22b are integrated by inserting them into the layers constituting the preform 10. Therefore, the preform is provided with a cutout in the thickness where the stiffener is installed, so that the two wing portions 22a, 22b fall between the two layers of the preform. Therefore, each wing part 22a, 22
b is covered by a part of the preform 10 extending to the center 24 of the stiffener. Similarly, the cover layer 16 is interrupted at the stiffener 20 and extends over the stiffener wings to the center 24. The preform 10 includes the cover layer 16 and the preform 1
It is held in the forming device 12 by a connection with a thread 30 passing through the hole 0 and passing through the hole 14 or at least a part thereof in the forming device. In the example shown in FIG.
2. A sewing line is formed which alternately passes between one side and the other side of the assembly comprising the preform 10 and the cover layer 16.

【００１３】糸３０はまた、スチフナ２０の翼部２２
ａ、２２ｂも通過してスチフナと予成形物との結合を確
保している。これは、スチフナの予成形物を前もって高
密度化あるいは強固化しなかった場合、あるいは結合糸
の縫い込みを妨げないよう高密度化が大きく制限された
場合である。予成形物のスチフナを高密度化しないので
あれば、この予成形物をパネルの予成形物１０上に保持
する道具が必要となることは言うまでもない。このよう
な保持道具（図示せず）は、他の場合にスチフナの予成
形物とパネルの予成形物１０双方の形状を保つために必
要となる道具に比較すれば、非常に簡易なものである。
これはスチフナの予成形物の強固化が終わるとすぐに取
り出される。[0013] The yarn 30 is also connected to the wings 22 of the stiffener 20.
a and 22b also pass to secure the connection between the stiffener and the preform. This is the case where the stiffener preform has not previously been densified or stiffened, or where densification has been severely limited so as not to hinder sewing of the binding thread. If the stiffeners of the preform are not densified, it goes without saying that a tool for holding the preform on the panel preform 10 is required. Such a holding tool (not shown) is very simple compared to tools that would otherwise be required to maintain the shape of both the stiffener preform and the panel preform 10. is there.
It is removed as soon as the stiffener preform has hardened.

【００１４】糸３０は、高密度化段階でも完全性を保つ
ことができるよう、炭素やセラミック材等の耐火材製で
ある。糸３０による縫いとじで、予成形物１０が成形装
置１２に対して成形され、予成形物１０上に所望の形状
を刷り込むことになる。さらに、糸３０に張力を加えて
予成形物１０を圧縮することも可能である。カバー層１
６は、均一な圧縮が得られるよう結合糸による応力を分
散させるのに役立つ。組立品はその後、浸透炉に入れら
れ化学的蒸気蒸着によって高密度化される。マトリック
スが炭化ケイ素等のセラミック材製の場合は、ＵＳ−Ａ
−４７５２５０３に記載されているように、化学的蒸気
蒸着工程を使って中間熱分解炭素又は窒化ホウ素蒸着に
よって繊維を被覆すると有利である。予成形物１０が強
固化されたら、浸透工程を中断して成形装置１２から予
成形物を分離し、カバー層１６を除去してもよい。その
ためには、まず結合糸３０を成形装置後部で破壊する。
必要であれば、スチフナの予成形物を保持するために使
用した道具も共に取り出す。The yarn 30 is made of a refractory material such as carbon or a ceramic material so that integrity can be maintained even during the densification stage. The preform 10 is formed on the forming device 12 by the stitching with the thread 30, and a desired shape is imprinted on the preform 10. Further, it is possible to compress the preform 10 by applying tension to the yarn 30. Cover layer 1
6 helps to distribute the stress from the binding yarn so as to obtain a uniform compression. The assembly is then placed in an infiltration furnace and densified by chemical vapor deposition. When the matrix is made of a ceramic material such as silicon carbide, US-A
It is advantageous to coat the fibers by intermediate pyrolytic carbon or boron nitride deposition using a chemical vapor deposition process, as described in -4752503. Once the preform 10 has been solidified, the infiltration step may be interrupted to separate the preform from the forming device 12 and remove the cover layer 16. To this end, the binding yarn 30 is first broken at the rear of the forming apparatus.
If necessary, remove the tool used to hold the stiffener preform.

【００１５】既に説明したように、予成形物１０とカバ
ー層１６を形成する材料の膨張率の違いにより、後者の
取り出しが容易となる。カバー層１６を取り出す際は、
その上の表面コーティングも同時に除去することで、予
成形物の他面１０ｂをさらにデスケーリングする必要を
なくす。カバー層１６は、同時に結合糸も破壊する道具
を使って引き剥がす。カバー層１６と性質が同一である
中間層１８を、成形装置１２と予成形物１０の間に設置
し、これを結合糸３０で横切らせることもできる。層１
８と予成形物１０の間及び層１８と成形装置１２の間の
境界面の破断により予成形物１０の型はずしや層１８自
身の除去が容易となる。これによって層１８上に形成さ
れた表面コーティングを除去し、予成形物の他面１０ｂ
をデスケーリングする必要をなくす。高密度化した予成
形物と保持道具と分離を容易にするという中間層の利用
は、１９９０年１１月２９日付けアメリカ合衆国特許出
願番号第６２０ １５７号に記載されている。そして、
必要な密度が得られるまで、予成形物１０及びスチフナ
２０からなる組立品の共高密度化を継続することができ
る。結合糸の残った部分は、パネルの績層間セン断抵抗
の増加に寄与する。As described above, the difference between the expansion rates of the materials forming the preform 10 and the cover layer 16 facilitates the removal of the latter. When removing the cover layer 16,
The surface coating thereon is also removed, eliminating the need for further descaling of the other side 10b of the preform. The cover layer 16 is peeled off using a tool that simultaneously destroys the binding yarn. An intermediate layer 18 having the same properties as the cover layer 16 can be provided between the molding device 12 and the preform 10 and traversed by the binding yarn 30. Tier 1
Breaking of the interface between the preform 10 and the preform 10 and between the layer 18 and the forming device 12 facilitates demolding of the preform 10 and removal of the layer 18 itself. This removes the surface coating formed on the layer 18 and the other side 10b of the preform.
Eliminates the need to descale. The use of an intermediate layer to facilitate separation of the densified preform and holding tool is described in U.S. Patent Application No. 620 157 dated November 29, 1990. And
Until the required density is obtained, the co-densification of the assembly comprising the preform 10 and the stiffener 20 can be continued. The remaining portion of the binding yarn contributes to an increase in the shear resistance of the panel between layers.

【００１６】図２に、一体式スチフナを装着したパネル
の製造に関する本発明の工程の他の実施例を示す。図２
でも、前もって中間層１８で覆い成形装置１２上に配置
した予成形物１０及び予成形物１０上のカバー層１６が
示されている。この例では、スチフナ４０（図２では１
つのみ示す）はＣ部側面からなる。スチフナは任意に高
密度化（強固化）することのできる繊維強化織物製であ
る。図２に示すように、各スチフナ４０は、その翼部４
２を予成形物１０の２つの層の間に嵌合させることで予
成形物１０と一体化しており、翼部４２が嵌合できるよ
う予成形物の厚み上部には切開部が形成されている。同
じく、カバー層１６はスチフナの位置で中断されてい
る。予成形物１０を糸５０によって成形装置１２上に設
置し、任意に圧縮する。糸５０は、図１の実施例に示し
たようにスチフナ４０と予成形物１０の間の結合を提供
することもできる。FIG. 2 shows another embodiment of the process of the present invention for manufacturing a panel with an integrated stiffener. FIG.
However, there is shown the preform 10 previously covered on the forming device 12 with the intermediate layer 18 and the cover layer 16 on the preform 10. In this example, the stiffener 40 (1 in FIG. 2)
Only one) is formed from the side surface of the portion C. The stiffener is made of a fiber reinforced fabric that can be optionally densified (consolidated). As shown in FIG. 2, each stiffener 40 has its wing 4
2 is integrated with the preform 10 by fitting it between the two layers of the preform 10, and a cutout is formed in the upper part of the thickness of the preform so that the wing 42 can be fitted. I have. Similarly, the cover layer 16 is interrupted at the stiffener. The preform 10 is placed on the forming device 12 with the yarn 50 and optionally compressed. Thread 50 may also provide a bond between stiffener 40 and preform 10 as shown in the embodiment of FIG.

【００１７】本実施例では、各糸５０は成形装置１２の
裏面を通り、穴１４又は少なくともこの穴のいくつかを
介して各回毎に輪５２を形成しながら、層１８、予成形
物１０及び層１６に縫い込まれる。糸５０がスチフナ４
０の位置で翼部５２を通るようにすることもできる。棒
５４は各輪５２の上端に係り、カバー層１６を押圧する
ことによって輪を閉塞する。棒５４は、予成形物の高密
度化中の気体及び高温による打撃に耐えるセラミック又
は金属製材料でできている。これらの棒５４には、輪５
２を閉塞するばかりでなく、糸５０による張力を分散さ
せる働きもある。糸５０による張力は、棒５４を多数回
転させることによって各輪５２の位置で調整し、図３に
示すように輪５２にねじりを生じさせることができる。In this embodiment, each yarn 50 passes through the backside of the forming device 12 and forms a loop 52 each time through the hole 14 or at least some of the holes, while forming the layer 18, the preform 10 and Sewn into layer 16. Thread 50 is stiffener 4
It is also possible to pass through the wing portion 52 at the zero position. The rod 54 is related to the upper end of each ring 52 and closes the ring by pressing the cover layer 16. The rod 54 is made of a ceramic or metallic material that resists the impact of gas and high temperatures during densification of the preform. These rods 54 include the ring 5
Not only does it block 2, but also has the function of dispersing the tension due to yarn 50. The tension of the thread 50 can be adjusted at the position of each wheel 52 by rotating the rod 54 a number of times, thereby causing the wheel 52 to twist as shown in FIG.

【００１８】図４に中空の針５６を示すが、これには糸
５０が導入され、成形装置１２の穴１４、及び層１８、
予成形物１０、層１６からなる組立品、あるいはスチフ
ナの翼部４２を通じて係り、輪５２を形成する。中空針
５６は開先加工端を有し、往復運動（矢印Ｆ）で変位さ
れながら穴を通過することによって予成形物に挿入され
る。FIG. 4 shows a hollow needle 56 into which the thread 50 has been introduced, the hole 14 in the forming device 12 and the layer 18,
A preform 10, an assembly of layers 16 or a stiffener wing 42 engages to form a ring 52. The hollow needle 56 has a beveled end and is inserted into the preform by passing through the hole while being displaced in a reciprocating motion (arrow F).

【図面の簡単な説明】[Brief description of the drawings]

【図１】本発明の一体式スチフナを有する複合材構造パ
ネルの製造用繊維状予成形物の成形工程の一実施例を示
す部分略図である。FIG. 1 is a partial schematic view showing one embodiment of a forming step of a fibrous preform for manufacturing a composite structural panel having an integrated stiffener of the present invention.

【図２】本発明の工程の他の実施例を示す図である。FIG. 2 is a view showing another embodiment of the process of the present invention.

【図３】第２図の場合の予成形物の結合糸の張力調整を
示す図である。FIG. 3 is a view showing the tension adjustment of a binding yarn of a preformed product in the case of FIG. 2;

【図４】本発明の実施例における結合糸の設置方法を示
す図である。FIG. 4 is a view showing a method of installing a binding yarn in an embodiment of the present invention.

【符号の説明】[Explanation of symbols]

１０…予成形物 １２…成形装置 ２０…スチフナ ３０…糸 DESCRIPTION OF SYMBOLS 10 ... Pre-formed thing 12 ... Molding apparatus 20 ... Stiffener 30 ... Yarn

───────────────────────────────────────────────────── フロントページの続き (72)発明者 ジャン ルイ リムジン フランス国，33290−ル ピアン ムド, アレ モンテスキュー，ラ ミュザルデ ィエール（番地なし) (58)調査した分野(Int.Cl.7，ＤＢ名) C04B 35/80 ──────────────────────────────────────────────────の Continued on the front page (72) Inventor Jean-Louis Limousine 33290-Le Pianmud, Ares Montesquieu, La Musardieres (no address) (58) Fields investigated (Int. Cl. 7 , DB name) C04B 35/80

Claims (13)

(57)【特許請求の範囲】(57) [Claims] 【請求項１】 繊維状の予成形物（１０）を製造し、前
記予成形物（１０）を所望の圧縮度で所望の形状に保つ
ため前記予成形物（１０）を配置し、マトリックスを構
成する材料の化学的蒸気蒸着によって前記予成形物（１
０）を高密度化する段階から成る、マトリックスで高密
度化した繊維状予成形物（１０）から成る熱構造的複合
材料部品の製造工程において、前記予成形物（１０）を
横切り成形装置（１２）の穴（１４）を通過する糸（３
０；５０）により、固定した成形装置（１２）に前記予
成形物（１０）を結合して前記予成形物（１０）を前記
配置することを特徴とする工程。1. A fibrous preform (10) is manufactured, said preform (10) is arranged to keep said preform (10) in a desired shape at a desired degree of compression, and a matrix is formed. The preform (1) is formed by chemical vapor deposition of the constituent materials.
0) in the process of producing a thermostructural composite part comprising a fibrous preform (10) densified with a matrix, comprising the step of densifying the preform (10). Thread (3) passing through hole (14)
0; 50), wherein the preform (10) is coupled to the fixed forming device (12) and the preform (10) is arranged. 【請求項２】 前記結合を、炭素及びセラミックの中か
ら選んだ材料製の糸（３０；５０）によって行うことを
特徴とする請求項１記載の工程。2. The process according to claim 1, wherein the bonding is performed by means of a thread made of a material selected from the group consisting of carbon and ceramic. 【請求項３】 前記予成形物（１０）の前記結合の前
に、予成形物（１０）の前記成形装置（１２）に向けた
面とは反対の表面上にカバー層（１６）を配置すること
を特徴とする請求項１又は２のいずれかに記載の工程。3. A cover layer (16) is arranged on the surface of the preform (10) opposite to the surface of the preform (10) facing the forming device (12) before the joining of the preform (10). The process according to claim 1, wherein the process is performed. 【請求項４】 前記カバー層（１６）が布製であること
を特徴とする請求項３記載の工程。4. The process according to claim 3, wherein the cover layer is made of cloth. 【請求項５】 前記カバー層（１６）は、前記予成形物
（１０）を構成する前記材料とは異なる膨張率を有する
材料製であることを特徴とする請求項３又は４のいずれ
かに記載の工程。5. The method according to claim 3, wherein the cover layer is made of a material having an expansion coefficient different from that of the material forming the preform. The described steps. 【請求項６】 前記予成形物（１０）と前記成形装置
（１２）との間に中間層（１８）を配置することを特徴
とする請求項１から５のいずれかに記載の工程。6. The process according to claim 1, wherein an intermediate layer (18) is arranged between the preform (10) and the molding device (12). 【請求項７】 多数の要素を、前記結合糸（３０；５
０）で結合することによって前記予成形物（１０）に一
体化させることを特徴とする請求項１から６のいずれか
に記載の工程。7. A method according to claim 1, wherein a number of elements are connected to said binding yarn (30; 5).
7. The process according to claim 1, wherein the preform is integrated with the preform by bonding at 0). 【請求項８】 部分的に高密度化した繊維状織物ででき
た側面要素からなる一体式スチフナが装着され何層にも
重ねた織物状部品の製造に適用される工程において、前
記予成形物の厚みの一部に形成した切開部を介して前記
予成形物の２層間に前記スチフナの少なくとも１翼部を
挿入することによって各スチフナを前記予成形物と一体
化することを特徴とする請求項７記載の工程。8. The process according to claim 1, wherein the preform is applied to the production of a multi-layered woven part fitted with an integral stiffener comprising side elements made of a partially densified fibrous woven fabric. Wherein each stiffener is integrated with the preform by inserting at least one wing of the stiffener between two layers of the preform through a cutout formed in a portion of the thickness of the stiffener. Item 7. The process according to Item 7. 【請求項９】 各スチフナの翼部を通過する結合糸（３
０；５０）によって各スチフナが前記予成形物（１０）
に結合することを特徴とする請求項８記載の工程。9. A binding yarn (3) passing through the wings of each stiffener.
0; 50) so that each stiffener is a preform (10)
9. The process according to claim 8, wherein the method is combined with 【請求項１０】 各結合糸は、縫いとじによって前記成
形装置（１２）の穴と前記予成形物（１０）に挿入され
ることを特徴とする請求項１から９のいずれかに記載の
工程。10. The process according to claim 1, wherein each binding thread is inserted into a hole of the forming device and the preform by means of a stitch. . 【請求項１１】 各結合糸は、前記成形装置（１２）の
前記穴（１４）と前記予成形物（１０）に導入されて各
縫い目で輪を形成し、輪に挿入されて前記予成形物（１
０）を押圧する棒によって前記輪が閉塞されることを特
徴とする請求項１から９のいずれかに記載の工程。11. Each binding yarn is introduced into the hole (14) of the forming device (12) and the preform (10) to form a loop at each seam, and is inserted into the loop to form the preform. Things (1
10. The process according to claim 1, wherein the ring is closed by a rod pressing 0). 【請求項１２】 前記結合糸（３０；５０）の張力は、
前記棒を使って前記輪（５２）をねじることによって調
整することを特徴とする請求項１１記載の工程。12. The tension of the binding yarn (30; 50) is
The process according to claim 11, wherein the adjustment is performed by twisting the hoop (52) with the rod. 【請求項１３】 前記結合糸（３０；５０）は、中空針
によって前記成形装置（１２）の穴（１４）及び前記予
成形物（１０）に導入されることを特徴とする請求項１
０又は１１のいずれかに記載の工程。13. The forming thread (30; 50) is introduced into the hole (14) of the forming device (12) and the preform (10) by a hollow needle.
12. The process according to any of 0 or 11.
JP03076446A 1990-04-09 1991-04-09 Molding process of preforms for the production of thermostructural composite parts, in particular woven parts or panels Expired - Fee Related JP3095180B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9004535A FR2660591B1 (en) 1990-04-09 1990-04-09 PROCESS FOR CONFORMING PREFORMS FOR THE MANUFACTURE OF PARTS OF THERMOSTRUCTURAL COMPOSITE MATERIAL, PARTICULARLY OF PARTS IN THE FORM OF SAILS OR PANELS.
FR9004535 1990-04-09

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JPH04224177A JPH04224177A (en) 1992-08-13
JP3095180B2 true JP3095180B2 (en) 2000-10-03

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US20050093188A1 (en) * 2003-10-29 2005-05-05 Forest Mark L.L. Binderless preform manufacture
JP2005205902A (en) * 2003-12-22 2005-08-04 General Electric Co <Ge> Ceramic matrix composite material having improved layer strength and method therefor
US8357323B2 (en) * 2008-07-16 2013-01-22 Siemens Energy, Inc. Ceramic matrix composite wall with post laminate stitching
US20120202003A1 (en) * 2011-02-08 2012-08-09 Mcenerney Bryan William Composite article, method and equipment therefor
WO2013063703A1 (en) * 2011-11-03 2013-05-10 Groupe Ctt Inc. Method of manufacturing weaved preform with oriented weft yarns
US10618848B2 (en) 2013-09-20 2020-04-14 General Electric Company Ceramic matrix composites made by chemical vapor infiltration and methods of manufacture thereof
FR3026675B1 (en) * 2014-10-02 2016-11-11 Mbda France PROCESS FOR THE PRODUCTION OF A DOUBLE-WALL THERMOSTRUCTURAL COMPOSITE MONOLITHIC PIECE AND PART OBTAINED
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FR2567874B1 (en) * 1984-07-20 1987-01-02 Europ Propulsion PROCESS FOR MANUFACTURING A COMPOSITE MATERIAL WITH REFRACTORY FIBROUS REINFORCEMENT AND CERAMIC MATRIX, AND STRUCTURE AS OBTAINED BY THIS PROCESS
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EP0452199B1 (en) 1995-03-22
JPH04224177A (en) 1992-08-13
US5160471A (en) 1992-11-03
DE69108279D1 (en) 1995-04-27
FR2660591A1 (en) 1991-10-11
DE69108279T2 (en) 1995-11-09
CA2039345A1 (en) 1991-10-10
EP0452199A1 (en) 1991-10-16
CA2039345C (en) 1997-10-07
FR2660591B1 (en) 1992-08-14

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